CN109279013B - Unmanned ground effect aircraft with slideway type adjusting device - Google Patents

Abstract

The invention provides an unmanned ground effect aircraft with a slideway type adjusting device. The invention comprises an unmanned ground effect aircraft body and a slideway type adjusting device arranged on a central longitudinal axis in the unmanned ground effect aircraft body, wherein the slideway type adjusting device comprises: the device comprises a fixed shaft, a movable slide block, a traction chain, a hydraulic mechanism and a gyroscope. The invention effectively solves the problems of overlarge take-off power caused by overlong sliding distance and insufficient lift force of the ground effect wing aircraft in the take-off stage by the slideway type adjusting device arranged in the unmanned ground effect aircraft; the problem of stall of the aircraft caused by overlarge elevation angle in the moment of departure from the water surface in the departure stage is also effectively solved, so that the ground effect wing aircraft takes off in a short time and in a short distance before reaching a resistance peak, the stability and the safety in the departure process are ensured, and the device is simple and quick to install.

Description

An unmanned ground-effect aircraft with a slide-type adjustment device

Technical field

The present invention relates to the technical field of ground effect aircraft, and specifically, to an unmanned ground effect aircraft with a slide-type adjustment device.

Background technique

The ground effect aircraft is a new type of high-speed ship that uses ground effect wings to generate additional lift. It has a large lift-to-drag ratio and ultra-low-altitude high-speed cruising capabilities. It is a new type of high-speed ship between an airplane and a conventional displacement ship. It has advantages that ordinary ships cannot match. Seakeeping and high navigation performance are widely used in military and civilian fields, and the market prospects are broad. It has become one of the hot spots in international ship development in recent years.

Although various countries have made rapid progress in research on ground-effect wing craft in recent years and solved many technical problems, there are still many problems that need further improvement and perfection. First, there is a drag peak in the hydrodynamic performance of the ground-effect wing aircraft. The drag peak is when the aircraft takes off in a floating state. When the speed increases, the drag gradually increases. At this time, the pitch angle increases, the aircraft begins to raise its head, and the hydrodynamic lift gradually increases. , the draft decreases, and the resistance reaches the maximum value at this time, forming a resistance peak. Therefore, only when the thrust of the main engine exceeds the resistance peak can the aircraft escape from the water. But even so, as the speed further increases, the hydrodynamic force of the ground-effect wing aircraft disappears when it leaves the water, and the resistance due to the aerodynamic force changes suddenly. Due to the large pitch angle of take-off, it is easy to fly high quickly or even stall, causing unpredictable and serious consequences. To sum up, in the current development process of wing-in-surface effect craft, the following two technical problems must be solved:

(1) The resistance peak value during take-off is large and the required take-off distance is long, making it impossible for the hull to lift out of the water quickly;

(2) The moment the aircraft leaves the water, it flies high quickly or stalls due to the excessive pitch angle.

To address the above problems, we currently only focus on the engine power and ground-effect wing body line shape to increase the engine power and provide greater thrust to reach and cross the resistance peak. However, this increases the weight of the aircraft and weakens the carrying capacity. performance, and the cost is greatly increased; in addition, the position of the step is controlled to control the nose-up torque and balance the proportion of engine power and take-off angle of attack, but the control scale is difficult to grasp and the control effect is not good.

Contents of the invention

According to the technical problems raised above, an unmanned ground effect aircraft with a slide-type adjustment device is provided. Through the slide-type adjustment device provided by the present invention, the sliding distance of the unmanned ground-effect aircraft can be shortened during the taxiing phase, the take-off efficiency can be improved, and the stability of the flight phase can be improved at the same time.

The technical means adopted in the present invention are as follows:

An unmanned ground-effect aircraft with a slide-type adjustment device, including an unmanned ground-effect aircraft body and a slide-type adjustment device arranged on the longitudinal axis inside the body of the unmanned ground-effect aircraft, the slide-type adjustment device The adjustment device includes: fixed shaft, moving slider, traction chain, hydraulic mechanism and gyroscope.

The fixed shaft is longitudinally installed on the central longitudinal axis inside the unmanned ground effect aircraft, and a guide groove is provided in the horizontal direction of the fixed shaft. A slide groove that matches the shape of the guide groove is provided inside the moving slider, so that the movement The slider can move along the fixed axis, and holes matching the traction chain are also opened inside the mobile slider. The upper/lower side openings are traction holes that match the shape of the traction chain, and the holes on the other side are apertures. A through hole larger than the diameter of the traction chain. There are two hydraulic mechanisms and they are respectively fixed at both ends of the fixed shaft. The traction chain surrounds the two hydraulic mechanisms and is used to capture the gyro of the flight status signal in real time. The instrument is installed inside the unmanned ground effect aircraft. The hydraulic mechanism is equipped with a communication device and a controller that accepts gyroscope signals. After analysis by the controller program, the information to be adjusted is transmitted to the hydraulic mechanism. The hydraulic mechanism drives the traction chain. Automatically adjust the longitudinal position of the slider on the fixed shaft.

Further, the hydraulic mechanism includes a hydraulic device, a roller and a transmission shaft. The hydraulic device is fixed on the end of the fixed shaft. The roller is connected to the hydraulic device through the transmission shaft. The traction chain is mounted on the roller. The roller rotates and pulls the slider to move longitudinally through the traction chain.

Furthermore, each hydraulic mechanism has two rollers which are symmetrically arranged on both sides of the hydraulic device, and there are two traction chains.

Further, the hydraulic device is a two-way hydraulic pump.

Furthermore, the fixed shaft has an I-shaped vertical cross-section after the guide groove is provided, and the upper and lower sides of the I-shape are parallel to the horizontal plane.

Further, the top and bottom of the slide groove are parallel to the horizontal plane, and a first gap of preset height is left between the top of the slide groove and the upper edge of the guide groove. There is a second gap with a preset height between them, and rolling bearings are installed at the top and bottom of the slide groove.

Further, the first gap and the second gap have the same height, and the rolling bearing installed at the top of the slide groove and the rolling bearing installed at the bottom of the slide groove have the same specifications.

Furthermore, there are four rolling bearings installed at the top of the slide groove and four rolling bearings installed at the bottom of the slide groove, and they are arranged symmetrically.

Further, the gyroscope and the hydraulic mechanism communicate through wireless signals.

Compared with the prior art, the present invention has the following advantages:

1. The vertical cross-section of the fixed shaft is "I"-shaped, which fully allows the moving slider and the fixed shaft to naturally engage, greatly improving the stability and safety of the device, and the "I"-shaped cross-section of the same material is resistant to The bending section coefficient is larger, the strength is high and the material is saved, maximizing the benefits of the device;

2. The moving slider does not move along the fixed axis entirely by bite force, but contacts the fixed axis through rolling bearings. Four rolling bearings are installed on the upper and lower surfaces of the slider to convert sliding friction into rolling friction, which has great performance in terms of energy saving and noise reduction. improve;

3. A two-way hydraulic pump is used to output the driving force, and through the rollers and four traction chains, the slider is evenly stressed and the longitudinal movement is smooth;

4. In order to realize automatic adjustment of flight status, a sensing gyroscope device is installed. This device is used in the automatic control system of aircraft movement. It serves as a horizontal, vertical, pitch, heading and angular velocity sensor to transmit the captured flight status signals to The entire slide-type adjustment device realizes automatic adjustment function.

The present invention effectively solves the problem of excessive taxiing distance and insufficient lift of the ground-effect wing aircraft during the take-off phase, which in turn leads to excessive take-off power, through a slide-type adjustment device provided inside the unmanned ground-effect aircraft; it also effectively solves the problem of excessive take-off power during the take-off phase. At the moment of leaving the water, the aircraft stalls due to excessive elevation angle, allowing the ground-effect wing aircraft to take off in a short time and a short distance before reaching the resistance peak, ensuring stability and safety during flight, and the installation of the device is simple and fast.

Based on the above reasons, the present invention can be widely promoted in the technical field of ground effect aircraft.

Description of drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that need to be used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings in the following description These are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without exerting any creative effort.

Figure 1 is a schematic side view of the structure of the present invention.

Figure 2 is a schematic top view of the structure of the present invention.

Figure 3 is a schematic front view of the structure of the present invention.

In the picture: 1. Fixed shaft, 2. Moving slider, 3. Traction chain, 4. Hydraulic device, 5. Gyroscope, 6. Rolling bearing, 7. Roller, 8. Transmission shaft, 9. Unmanned ground effect vehicle body , 10. Traction hole; 11. Through hole; 12. First gap; 13. Second gap; 14. Upper edge of guide groove; 15. Lower edge of guide groove; 16. Top of slide groove; 17. Slide concave bottom of the tank.

Detailed ways

It should be noted that, as long as there is no conflict, the embodiments and features in the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and embodiments.

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments These are only some embodiments of the present invention, rather than all embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application or uses. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts fall within the scope of protection of the present invention.

It should be noted that the terms used herein are for the purpose of describing specific embodiments only, and are not intended to limit the exemplary embodiments according to the present invention. As used herein, the singular forms are also intended to include the plural forms unless the context clearly indicates otherwise. Furthermore, it will be understood that when the terms "comprises" and/or "includes" are used in this specification, they indicate There are features, steps, operations, means, components and/or combinations thereof.

The relative arrangement of components and steps, numerical expressions, and numerical values set forth in these examples do not limit the scope of the invention unless specifically stated otherwise. At the same time, it should be understood that, for convenience of description, the dimensions of various parts shown in the drawings are not drawn according to actual proportional relationships. Techniques, methods and equipment known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, such techniques, methods and equipment should be considered part of the authorized specification. In all examples shown and discussed herein, any specific values are to be interpreted as illustrative only and not as limitations. Accordingly, other examples of the exemplary embodiments may have different values. It should be noted that similar reference numerals and letters refer to similar items in the following figures, so that once an item is defined in one figure, it does not need further discussion in subsequent figures.

In the description of the present invention, it should be understood that the orientation indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, vertical, horizontal" and "top, bottom" etc. Or the positional relationship is usually based on the orientation or positional relationship shown in the drawings, which are only for the convenience of describing the present invention and simplifying the description. Without explanation to the contrary, these directional words do not indicate and imply the referred devices or components. Must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be construed as limiting the scope of the invention: the orientation words "inside and outside" refer to the inside and outside relative to the outline of each component itself.

For the convenience of description, spatially relative terms can be used here, such as "on...", "on...", "on the upper surface of...", "above", etc., to describe what is shown in the figure. The spatial relationship between one device or feature and other devices or features. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a feature in the figure is turned upside down, then one feature described as "above" or "on top of" other features or features would then be oriented "below" or "below" the other features or features. It lies beneath the device or structure." Thus, the exemplary term "over" may include both orientations "above" and "below." The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

In addition, it should be noted that the use of words such as "first" and "second" to define parts is only to facilitate the distinction between corresponding parts. Unless otherwise stated, the above words have no special meaning and therefore cannot be understood. To limit the scope of protection of the present invention.

As shown in Figures 1 and 2, the present invention provides an unmanned ground effect aircraft with a slide-type adjustment device, including an unmanned ground effect aircraft body and a central longitudinal axis arranged inside the unmanned ground effect aircraft body. The slide-type adjustment device on the aircraft. In the field of aircraft and ships, such as airplanes, the direction from the nose to the tail is longitudinal.

The slide-type adjustment device includes: a fixed shaft 1, a moving slider 2, a traction chain 3, a hydraulic mechanism and a gyroscope 5,

The fixed shaft 1 is installed longitudinally on the central longitudinal axis inside the unmanned ground effect aircraft, and is specifically arranged in the equipment cabin of the aircraft. The fixed shaft 1 is provided with guide grooves in the horizontal direction, and the moving slider 2 is provided with a guide groove inside. The slide groove with matching guide groove shape allows the mobile slider 2 to move along the fixed axis 1. There are also holes matching the traction chain 3 inside the mobile slider 2, where the upper/lower side openings are The traction hole 10 matches the shape of the traction chain 3, and the opening on the other side is a through hole 11 with a diameter larger than the diameter of the traction chain 3. There are two hydraulic mechanisms and they are respectively fixed to both ends of the fixed shaft 1. The traction chain 3 surrounds two hydraulic mechanisms. The gyroscope 5 used to capture flight status signals in real time is located inside the unmanned ground effect aircraft. The hydraulic mechanism is provided with a communication device and control device that receives signals from the gyroscope 5 After analysis by the controller program, the information to be adjusted is transmitted to the hydraulic mechanism. The hydraulic mechanism drives the traction chain 3 and automatically adjusts the longitudinal position of the moving slider 2 on the fixed shaft 1. The gyroscope 5 communicates with the hydraulic mechanism through wireless signals. The moving slider 2 changes the overall weight and center of gravity distribution of the ground-effect wing aircraft through longitudinal movement, thereby redistributing the weight, thereby changing the pitch angle of the aircraft.

Gyroscope 5 is used in the automatic control system of aircraft movement. As a horizontal, vertical, pitch, heading and angular velocity sensor, it transmits the captured flight status signal to the entire slide adjustment device to realize the automatic adjustment function. The gyroscope 5 is installed in the control room of the aircraft. The data detected by the gyroscope 5 is transmitted through wireless signals. There is a signal receiving device on the hydraulic device 4. After analysis by the controller program, the information to be adjusted (such as moving the slider 2 Moving forward or backward, moving distance, etc.) are transmitted to the hydraulic device 4. The control is completely automatic by the controller and does not require human control.

The hydraulic mechanism provides driving force for the entire device, which includes a hydraulic device 4, a roller 7 and a transmission shaft 8. The hydraulic device 4 is fixed to the end of the fixed shaft 1, and the roller 7 passes through the transmission shaft 8. Connected to the hydraulic device 4, the traction chain 3 is mounted on the roller 7. The roller 7 rotates and pulls the sliding block 2 to move longitudinally through the traction chain 3. There are two rollers 7 of each hydraulic mechanism and they are symmetrically arranged on both sides of the hydraulic device 4, and there are two traction chains 3. The hydraulic device 4 is a two-way hydraulic pump. The roller 7 carries the traction chain 3 and integrates the driving device and the traction device into a whole. Driven by the hydraulic device 4, it transmits energy to the traction chain 3.

As shown in Figure 3, the fixed shaft 1 has an I-shaped vertical cross-section after the guide groove is opened, and the upper side 14 and the lower side 15 of the I-shape are parallel to the horizontal plane. In consideration of the sliding stability between the fixed shaft 1 and the moving slider 2 and the strength of the fixed shaft during movement, the cross-sectional shape of the fixed shaft 1 is designed to be an "I" shape. The "I" shape can fully make the movable slider 2 and the fixed shaft 1 naturally mesh, greatly improving the stability and safety of the device, and the "I" shape section of the same material has a larger bending section coefficient. High strength and material saving, maximizing the benefits of the device.

The top 16 and bottom 17 of the slide groove are both parallel to the horizontal plane. There is a first gap 12 of a preset height between the top 16 of the slide groove and the upper edge 14 of the guide groove. A second gap 13 with a preset height is left between the lower edges 15 , and rolling bearings 6 are installed on both the top 16 and the bottom 17 of the slide groove. The first gap 12 and the second gap 13 have the same height, and the rolling bearing installed at the top 16 of the slide groove has the same specifications as the rolling bearing installed at the bottom of the slide groove. The number of rolling bearings installed on the top 16 of the slide groove and the rolling bearings installed on the bottom 17 of the slide groove are four and symmetrically arranged. The sliding friction between the moving slider 2 and the fixed shaft 1 is converted into rolling friction, saving energy and reducing noise. Performance has been greatly improved.

In summary, the present invention can solve the problems of the ground-effect wing aircraft provided by the prior art in the take-off phase, such as long taxiing distance, long take-off time, high power consumption of the main engine, and stalling caused by excessive elevation angle when it leaves the water. The present invention has more advantages. It can effectively reduce the main engine power required for take-off, achieve short-distance rapid take-off and prevent stalling, so that the ground-effect wing aircraft can obtain sufficient speed and lift before the resistance peak, stabilize the flight state and reduce landing impact, and the design is simple Easy to install.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention, but not to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: The technical solutions described in the foregoing embodiments can still be modified, or some or all of the technical features can be equivalently replaced; and these modifications or substitutions do not deviate from the essence of the corresponding technical solutions from the technical solutions of the embodiments of the present invention. scope.

Claims (4)

1. Unmanned ground effect aircraft with slide formula adjusting device, a serial communication port, including unmanned ground effect aircraft body and set up in slide formula adjusting device on the inside middle longitudinal axis of unmanned ground effect aircraft body, slide formula adjusting device includes: a fixed shaft, a movable slide block, a traction chain, a hydraulic mechanism and a gyroscope,

the fixed shaft is longitudinally arranged on a middle vertical axis in the unmanned ground effect aircraft, a guide groove is formed in the horizontal direction of the fixed shaft, a slideway groove matched with the guide groove in shape is formed in the movable sliding block, the movable sliding block can move along the fixed shaft, a hole matched with the traction chain is formed in the movable sliding block, wherein the hole on the upper side/lower side is a traction hole matched with the traction chain in shape, the hole on the other side is a through hole with the diameter larger than the diameter of the traction chain, the two hydraulic mechanisms are respectively fixed at two ends of the fixed shaft, the traction chain surrounds the two hydraulic mechanisms, the gyroscope for capturing flight state signals in real time is arranged in the unmanned ground effect aircraft, a communication device and a controller for receiving the gyroscope signals are arranged on the hydraulic mechanism, the information to be adjusted is transmitted to the hydraulic mechanism through analysis of a controller program, the hydraulic mechanism drives the traction chain, and the longitudinal position of the sliding block on the fixed shaft is automatically adjusted;

the hydraulic mechanism comprises a hydraulic device, a roller and a transmission shaft, the hydraulic device is fixed at the end part of the fixed shaft, the roller is connected with the hydraulic device through the transmission shaft, the traction chain is carried on the roller, and the roller rotates to drag the movable sliding block to longitudinally move through the traction chain;

the vertical section of the fixing shaft is I-shaped after the fixing shaft is provided with the guide groove, and the upper edge part and the lower edge part of the I-shape are parallel to the horizontal plane;

the top and the bottom of the slideway groove are parallel to the horizontal plane, a first gap with a preset height is reserved between the top of the slideway groove and the upper edge of the guide groove, a second gap with a preset height is reserved between the bottom of the slideway groove and the lower edge of the guide groove, and rolling bearings are arranged at the top and the bottom of the slideway groove;

the heights of the first gap and the second gap are the same, and the rolling bearing arranged at the top of the slideway groove and the rolling bearing arranged at the bottom of the slideway groove have the same specification;

the number of the rolling bearings arranged at the top of the slideway groove and the number of the rolling bearings arranged at the bottom of the slideway groove are 4 and are symmetrically distributed.

2. The unmanned ground effect vehicle with the slideway type adjusting device according to claim 1, wherein the number of the rollers of each hydraulic mechanism is two, the rollers are symmetrically arranged on two sides of the hydraulic device, and the number of the traction chains is two.

3. Unmanned ground-effect vehicle with a slide-type adjusting device according to claim 1 or 2, characterized in that the hydraulic device is a two-way hydraulic pump.

4. The unmanned ground effect vehicle having a slide way type adjusting device according to claim 1, wherein the gyroscope is in wireless signal communication with the hydraulic mechanism.